Braking device for aircraft



Jan. 12, 1932. R. MICEK' BRAKING DEVICE FOR AIRCRAFT Filed April 15, 19:50 GSheets-Sheet WWW Jan. 12, 1932. MICEK 1,840,592

BRAKING DEVICE FOR AIRCRAFT Filed A ril 15. 1950 s Sheets-meet 2 SW R. Micek Jan. 12, 19.32. R. MICEK 1,840,592

BRAKING DEVICE FOR AIRCRAFT Filed April 15, 1950 6 Sheets-Sheet 3 nag Jan. 12, 1932. R. MICEK BRAKING DEVICE FOR AIRCRAFT Filed. April 15, 1930 6 Sheefis-Sheet 4 awwm/boz RlMicek Jan. 12,- 1932. R. MICEK BRAKING DEVICE FOR AIRCRAFT Filed April 15. 1930 6 Sheets-Sheet 5 Jam-12, 1932;

R. MICEK 1,840,592 BRAKING DEVICE FOR AIRCRAFT Filed April 15, 1930 e Sheets-Sheet e Pus ies 'J n. 12, 1932 ND STATE r'rsm' oF ics G DEVICE FOR AIRCBAI'T Application filed April 15, 1930. Serial 30. 4,581.

Tnis'irwention relates to airplanes and has far an object to provide novel air foils which are nurmaiiy conceaied within the wing structure and'may be pasitiveiy pushed 01112- wsrtiiy 30 extend sxtsrioriy of the wing into v the siream at the moment the plane muches firs gronnci' 21115. serve as air "brakes t0 permirianciings in smaii fielcis and minimize airs yossifais accidents in landing.

A further objec is togmsvic'ie nsvei air foils which serve as air "brakes and M19 s0 built into the wirig structure as 119'; toiriterfere the stream line conissur of the Wings ir. snci which when is operative pssitisn an wil" curve "forwsrciiy ossr fins tmiiing eiiges 01 as wings and sci somewhat as miniasure skates is rs'isrii speed ti'ns ship in ism obg'sci; is so yrs-rifle ssvsi brakes on my Wings and which be sonvenien'biy ersrsi-sci by tire PEG; is ssisctirsiy iii s brakes 0n ans side w the 121s: vb-eras is assist bringing the pisrss a s i, spirs firth-s1 object 0:? the invention is $0 proawe sir brakes on the wings and nsrsi cantroliing means Ear applying "the brakes 61' ens :033 and bott m, 0:: an both Wings sop bottom on boifh Wings either is? si salrr may "be proniuceni as ssired by rigs para 50 cszrnrsi the position of she ship in m euvering.

' "he shave and ofiiisr objects in View may be rsserisd 1:0 v-ri bhin the scpps of th-e suspended claims wiishaui dessrting from the spirit as sacrificing any 0:? Ssirs afirantages of the inven'binn. V

lip. the, sccamg snying drawings forming pars sf fins specification,

Figure 1 is a piss View 0% a high-wing mnnepisns equippsi with my invention,

Figure 2 is s piss 'V'ifiW 0f the opsraiiing ievsr, operating rods, rock shafts, and push reds which csniroi the agrarian of the air fisiis or air brakes,

or boitqm whereby resistance to the air Figure 3- is a side elevation of she part-s sh wn in Fi re 2 with the parks dotted in 7 position to i: rust out the air foils,

Figure 4 is s iongituinal'sectionai view thrsugh the airplane wing taken on the line H of Figure 1,

Figura 5 is a, fragmentary lengitudinsi sectiena-l View similar ts Figure but showing the air foils *thrust anawariy and held in the air s'rsam $0 farm brakes,

Figure 6 is a. pian view sf a, passion of the Wing with the sever rammed t0 sxpcss im raved sir brake in rstraezsai @ssiisram,

Figure 7 is an erlsrgsfi issgitsxiinai sis-s3 tionai View firresgir the G8Ta2 i3ifig isvsr am?! adjacent Hf533 r Figurs 8 is an sniargs i 1am i'lfiudissi ssctisnsi View through the srizsnsinle trsrsvsrss member carris theisrsr fer mun-sci;

Ci the push r0615 to sfbiier Figurefi is s, crsss-ssciienai taker, the Zine 015 Figure 1G is er so, firs imam-19 as" r Fivurs 11 is a lsfihsii 5mg? 9 mews 1301* i027 jnstsci pnsitisns Wii-il rsspsss is 331s push roxis Fi re 12 is s eiasil :srsssssi e m A 1, shswmg one or 2 231E321 recis its sissrs and s stay i 01 2101" 51s :95. in "eirsctevil pesitisng V Figure 13 is s psrsssctivs r 'sr showing 0m sf the gush miis anl i as sprlrig s prssseri Making aisvies, Figure 14 is sirsgmsmsry crass ssct'erisi View when 031 the line l fa i 0i Figur arid showing 021s of the sir-bias hsiding 8331s foil in the air strssm, mi

Figure- 15 is a i'ragfmsmlsry psrs iscfiirs View showing s msfiifisfi fiorm sf air mil.

Referring now is 13 rswinfi in which like characters of rsfsrsme designate similar parts in the various views, a iiighwin mascpia-ne is i1iustratefi csmprislng a fuse sgs 10, Wings 11, siisrsns 12 or. 59 wing, tail co -tro1s 13, a motsr 14 am} a pmpsiier 15 these parts being 0f she usual and Wei snown construction; a

The invention resides more specifically in 10 structure as shown in the present embodiment "and the foil may open truss structure of the rear spar.

is provided both on the top surface and on the lower surface with the air brakes comrising the subject matter of this invention. ince all of the air brakes and their rating mechanism for both surfaces are uplicates of each other, the air brake on the upper surface of one wing will be described and reference numerals applied thereto and these reference numerals will be duplicated on the air brake on the bottom surface of the wing.

Referring now to Figures 4 and 5 the airplane wing structure 11 is shown to comprise ribs 16,.front and rear spars 17 and 18 preferably of metal truss construction, and a cover 19 which may be of treated fabric wood or metal. The ribs 16 are preferably depremed longitudinally as shown at 20 near the trailin portions thereof and the cover 19 is provide transversel with aslot 21 which communicates with t e rear ends of the de ressionsin the ribs.

11 air foil 22, as best shown in Figure 6, is slidably fitted in the depressions 20 of the ribs underneath the cover, preferably the air foil being composed of a, plurality of rigid slats 23, the longitudinal edges of which are hin edly connected to ether as shown at 24 so t at the air foil is exible." However, the

flexible air foil may be formed of a single sheet 25 of material, as best shown in Figure 15. In either case preferably light strong metal is employed in the construction of the air foil. The rear slat 26 in both the preferred and modified forms of the air fo1l is oif-set longitudinally and forms a closure for the slot 21 in the cover 19' so that the air foil will not interfere with the stream line contour of the wing during flight.

If desired the de 'ressionsmay be omitted mounted on ribs of ordinary construction. The flexible air foil may be positively pushed out into the air stream through the slot in the cover and for this purpose push rods 27 (see Figures 2 and 3) are connected to the inner edge portion of the airfoil and are connected to crank arms 28 carried by rock shafts 29 which are journaled in bearings 30 (see Figure 4) that are secured to the front spar 17. The push rods are operated from the pilots cockpit by mechanism which will be presently described in detail. Each push rod. is preferably passed through the push rods serve to push the flexib e air foil The bodily out of the slot 21 in the cover and into the air stream as best shown in Figure 5.

For securing the free edge portion of the air foilto the wing structure a plurality of cables 33 are secured to the rear edge portion of the air foil, these cables normally lying exteriorly of the wing structure u on the cover. The forward end of eac cable pisses through an opening 34 in the cover as st shown 1n Figures 14 and is referably connected to the rear spar, althoug the cable may be connected to the front spar if desired. Each cable is terminally equipped with a sprin 36 which bears against the front face 0 the spar and forms a shock absorber for the air foil.

The cables 33 bein substantially inextensible except for a sh ht lengthening under the compression of t e springs 36, cause the flexible air foil to curve forwardly into the air stream when in operative position,

and act somewhat as a miniature chute to retard speed of the ship in landing or during maneuvers as will he hereinafter more fully described. In addition to being shock absorbers the springs by compressing serve to place the center of pressure close to the cables when the air foils are open.

It will be noted by referrin to Figure 1 that the air foils are dispose between the ailerons 12 and the fuselage in the trailin edge portions of the wing and are controlle in ependently of the ailerons and are further operated selectively, that is the air brakes 22 may all be applied simultaneously as a unit or individually to suit varying requirements durin maneuvers or in landin v For rein orcing and strengthenm the wing structure to resist strain when t e air foils are open, a plurality of ribs 37 are arran ed outside of the cover and extend longitudlnall of the interior ribs 16 and are stream ine as shown. These exterior ribs 37 are rigidly secured preferably by bolts 37 to the front and rear spars and extend at their trailing edges substantially to the slot 21 in the cover so that when the air brake 22 is in operative position the air brake curves forwardly over the trail ends of the exterior ribs. The cover 37 extending from the front spar to the slot 21 may be attached ri 'dly to the outer-ribs 37 so as to lift off w on these ribs are removed to expose the air foil 22 and all working parts for inspection. The mechanism for operatin the push rods 27 to mani ulate the air br es will now be described. ferably arranged in the cockpit within convenient reach of the ilot there is a hollow lever 38, best shown in ig-' ures 3, 7 and 10.

The lower end of the lever terminates in a ball 39 which fits in a socket 40 and forms a pivot for the lever. The ball is normally at rest in the lower level of the socket and the ball in a seat 41 which also pivotally receives the ball. The weight of the lever is supported by a spring 41 disposed in the socket 40.

lhe lever is provided with a transverse cylindrical casing designated in general by the numeral 42 and best shown in Figure 8. Referring now to Figures 3 and 10 it will be seen that the casing 42 is'received in sleeves 43 formed on the rear ends of rods 44, the

7 front ends of which rods are connected by suitable link mechanisms 45 to the above'described crank shafts 29 which operate the push rods 27. This construction is clearly shown in Figures 2 and 3.

it is now clear that when the lever is rocked forwardly the rods 44 will be moved forwardly and through the instrumentality cf the link mechanisms 45 and rock shafts 29 will push the push rods 27 to thrust the air brakes 22 bodily into the air stream exteriorly whereby a pair of the air brakes may be opit will be sufiicient in length to connect to-- erated simultaneously. The casing, however, is made extensible as best shown in Figure 8, so that all of the sleeves may be enga ed by the casing to operate all'of the air bra es simultaneously when desired. To accomplish this the outer shell of the casing which is integral with the hollow lever as shown at 46, in Figure 7, slidably receives within its ends tubular casings 47 which are provided with integral washers 48 that fit in the threads of a worm 49. The worm has fixed thereto a pinion 50 which is held between stop discs 51 formed integral with the central portion of the outer shell and serves to rotate the worm. lhe washers 48 are provided with lugs 52 as best shown in Figure 9 which extend into the threads of the worm so that when the worm is operated both tubular casings 47 are simultaneously extended outwardly or retracted inwardly according to the direction of rotation of the worm.

The tubular casings 47 are held against rotation by means or pins 53 in the shell of the transverse casing fitting in slots 54in the tubular casings. tubular casings 47 are enlarged to rovide stop shoulders 55 which limit inwar movement of the tubular casings within the shell.

It will thus be seen that when the transverse casing 42 is extended as above described gether all of the sleeves 43. For extending The end portionsof the.

and retracting the extensible transverse casing 42 there is a rack 56 mounted to slide vertically within the hollow lever, as best shown in Figure 7 and engages a pinion 57 carried by the lever and which meshes with the pinion 50 which operates the worm 49.

The up i r end of the rack projects through the top 0 the lever and constitutes a grip 58 by means of which the rack may be moved downwardly to operate the worm. A helical spring 59 surrounds the rack and is confined between fixed discs 60 carried by the lever and through which the rack slides. This spring normally holds the rack in released position.

As best shown in Figure 2, the parts above described are disposed in centralized position to connect both air brakes on the top surfaces of the wings for simultaneous operation. Should it be desired to connect together the top and bottom air brakes of one wing alone for simultaneous operation the lever 38 must be shifted laterally to position the transverse casing 42 to connect one of the outer sleeves and one of the inner sleeves. Conversely, the top and bottom air brakes of the opposite wing may be connected by shifting the lever laterally in the opposite direction from that justdescribed.

For holding the lever in any desired adjusted position laterally with respect to the sleeves 43 an arcuate guide frame 62, best shown in Figures 11 and 10, is provided at the ends with trunnions 63 which are receivable in arcuate slots 64 formed in correspondingly shaped guides 65 that are secured sta' tionary at the ends of the guide frame. One side of the guide frame 62 is provided with a longitudinal angular recess 66 which receives an angular block 67 on the lever, (see Figure 7) and the opposite side of the guide frame is provided with a plurality of substantially semi-circular sockets 68 which selectively receive a semi-circular projection 69 on the lever as shown in Figure 7.

The sides of the guide frame 62 are Suficiently resilient to permit of the projection being dislodged from one socket and engaged in another socket when the lever is shifted laterally, to connect in desired combination any of the sleeves 43.

The rods44 arenormally locked against movement and to accomplish this, each rod 44 is provided with a lug 70, (see Fi ure 12) near its sleeve which lug engages t e front edge of a stop plate 71 positioned below the rod as best shown in Figure 3. To free the rods 44 the lever 38 must be lifted vertically to position the ball 39 in the seat 41 and when this is done the lug 70 is dislodged from the stop plate 71 asshown in dotted lines in Figure 3 so that the lever may now be rocked forwardly to operate the rods.

It will be observed by referring to Figure 3' that the arcuate slots 64 in the arcuate roe guides 65. are formed with lower seats 72 which normaHy receive the trunnions 63 of the guide frame 62 when the lever is in inactive position. When the lever is lifted to move the push rods and push out the air foils 22 the trunnions 63 on the guide frame 62 pass out of the seats 72 and into the arouate slot 64.

Referring now to Figures 2 and 13 it wil be seen that each rod 44 is receivable within a support 73 which is open at one side, all of these sup orts being mounted on a suitable frame 4. An angular member 75 is pivotally mounted as shown at 76 on the frame, one leg of the member entering the open side of the support 73 and bearing against the corresponding rod 44. The member 7 5 is frictionally held against the rod as will presently be described to hold the rod a ainst being dislodged from inoperative posltion due to vibration or other shocks or ars.

'As best shown in Figure 2 the angular members 75 are all connected to a cable 77 one end of which is secured by means of a sprin 78 to the frame 74and the opposite end 0 which is trained over sheaves 79 and- 80carried by the frame. The cable 77 is conducted through an opening in the ball 39 and enters. the hollow lever 38 as best shown in Figure 7. The cable is attached to a spring controlled pivoted latch 81. The latch 81 is o erated by the pilot to move the cable 77 agalnst the tension of the spring 78 and release the angular members The rack56 is provided with a stop 82 which engages with a latch 83 carried by the lever when the rack is depressed to extend the extensible transverse casing 42 as above described. When the stop 82 is in engagement with the latch 83 the transverse casing is held extended.

a It will be observed that the spring 78 (see Figure 2) is under suflicienttension to prevent slack occurring in the cable 77 at any position of the lever.

In operation, when it is desired to land in a small area all of the air brakes may be thrust out into the air stream simultaneously just at the moment the ship touches the ground. To accomplish this, first the member 58 is forced down and is held down by the latch 83. Thus, the transverse casing is extended and connects together all of the sleeves and the push rods, the inner rods bending to permit of this connection. Now the lever is raised to free all of the stop lugs 70 from the stop plates 71. Then the lever is rocked forwardly to push out the air brakes to whatever extent is needed. The

cables 33 as above described lift up over the run which is so unsafe in making emergency landings.

It Wlll be understood that the pilot may apply only the brakes on the top surfaces of the wings should he deem this sufiicient to effect a safe landin I While maneuvering the plane in flight should it be necessary to bring the plane out of a flat spin the air brakes on the hi h wing, either top or bottom surfaces, may applied by shifting the lever laterally to connect for simultaneous operation, the air brakes on the hi h wing. The resistance thus offered by t e high wing to the air stream will serve to level the wings.

A further object of the use of these air brakes is that a plane so equipped will stop sooner in landing than one equi ped with wheel brakes because these air bra es can be used effectively long before wheel brakes will possibly take effect or canbe used.

The air brakes also it will be observed constitute means for getting a plane out of a flat spin or auto-rotation by applfying the brakes to the wing on the outside 0 rotation.

It will further be observed that a shorter turn in flight may be made by use of these air brakes to avoid an obstruction or another plane.

Furthermore, in caseof drift the brakes on the wing towards the wind can be ap lied slightly so that the slight resistance 0 one wing over the other will maintain the plane on its true course.

Furthermore, greater maneuverability is provided under combat conditions and'also it will be apparent that the use of these air brakes will prevent a plane from nosing over on landing on rough ground as well as providing means for assistin a plane out of a ;tail spin by applying the rakes on the tops of both win Having ti us described the invention, I claim:

1. An air brake for airshi s comprising a wing, an air foil formed 0 slats disposed longitudinally of the wing and hinged together at their lon 'tudinal edges and normally concealed wit in the wing, and means for moving said air foil to operative position in the air stream exteriorly of the wing.

2. An air brake for airships comprising a wing, a flexible air foil slidably mounted near the trailing edge portion of the wing, means for positively pushing said air foil out into the air stream, and means securing the air foil to the wing structure whereby the air foil curves forwardly when in operative position.

3. The combination with the fuselage, wings and ailerons of an airplane, of flexible air brakes comprising air foils slidably mounted on the wings between the ailerons and fuselage and means for positively curving the air foils forwardly selectively into the air stream.

4. In an airplane wing structure, ribs, spars, a cover therefor, an air foil slidably fitted on said ribsand underneath said cover, means for moving said air foil to operative position outside of said cover and means connecting the outer edge of the air foil to one of the air foil normally closing said slot, and

means for moving said air foil to operative position through said slot.

6. in an airplane wing, an air brake comprising a flexible air foil housed within the wing structure, rods attached to the air foil for thrusting the air foil outwardly to project exteriorly of the wing, and cables attached to the wing and to the air foil and operating simultaneously with the rods to hold the air foil curved forwardly towards the leading edge of the wing.

7. lln combination, a wing, spaced stream line ribs disposed exteriorly of the wing for stifi'ening the wing, a flexible air foil normally housed within the wing structure and adapted to be thrust out into the air stream over the trailing ends of said stream line ribs, and means for manipulating said air toil.

8. In an airplane wing, ribs having depressions near the rear ends, a cover having a transverse slot communicating with the rear ends of said depressions in said ribs, a flexible air foil slidably mounted in said depressions in said ribs and adapted to pass outwardly through the slot in said cover and project I into the air stream, and means for manipulating said air foil.

9. In an airplane wing, ribs, a spar, a cover, an air foil slidably fitted on said ribs and adapted to be pushed outwardly through said cover into the air stream, means for pushing said air foil outwardly, a flexible cable disposed exteriorly of the wing and having one end connected to the free edge of the air foil for holding the air foil in the air stream, the outer end of said cable extending through openings in said cover and in said spar, and-a spring on the last named end of said cable bearing against said spar Eng forming a shock absorber for said air it In an airplane, air foils formed of jointed slats extending longitudinally of the wing structure and normally housed within the wing structure and adapted to be slid outwardly into the air stream to form air brakes, a pivoted lever, push rods operated by the lever for sliding said air foils into and out of the air stream, cables connecting the free edges of the foils to the win structure to curve said foils forwardly w on thrust into the air stream, and means operatively connecting the rods to the lever whereby the air foils may be selectively operated.

11; In an airplane, air foils carried by the wings and adapted to be slid outwardly into the air stream to form air brakes, sliding rods for moving the air foils to operative position, a pivoted lever adapted to slide said rods, said lever being shiftable laterally with respect to said rods, and a member carried by said lever adapted to connect together selected rods in pairs whereby the ah foils may be selectively operated in pairs.

12. In an airplane, air foils carried by the wings and adapted to be slid outwardly into the air stream to form air brakes above and below the wings, sliding rods for manipulating respective air foils, a pivoted lever for sliding the rods, an extensible member carried by the lever for selectively connecting together a plurality of said rods, and means for extending said member to connect together all of said rods to operate all of said air foils as a unit.

13. In an airplane, air foils carried by the wings and adapted. to he slid outwardly into the air stream to form air brakes, rods for manipulating the air foils, each rod terminating in a sleeve, a lever, and a transverse member carried by the lever and adapted to be selectively engaged in said sleeves to operate said rods.

14. In an airplane, air foils carried by the wings and adapted to he slid outwardly into the air stream toform air brakes, rods for operating the air foils terminating in sleeves, stops engaging said rods and holding said air foils retracted, a pivoted lever ada ted to be shifted laterally and adapted to e raised vertically, and a transverse member on said lever adapted to be engaged in said sleeves when the lever is moved laterally and adapt ed to release said rods from said stops when said lever is raised vertically after being ongaged in said sleeves.

15. In an airplane, air foils carried by the wings and adapted to be slid outwardly into the air stream to form air brakes, rods for sliding said air. foils terminating in sleeves, a lever, a transverse member for selectively connecting said sleeves and having extensible end portions for connecting additional sleeves to said selected sleeves, a pinion and worm devicecarried by said transverse mem her for extending said end portions thereof, and a rack and pinion device carried by said lever for operating said pinion and worm device. a

16. In an airplane, air foils carried by the wings and adapted to he slid outwardly into lid 'the'air stream to form air brakes, rods for sliding said air foils, a pivoted lever havin a transverse portion adapted to connect sai rods, said lever being movable laterally to selectively connect said rods, and means for holding said lever in various adjusted positions. 7

17. In an airplane, air foils carried by the wings and adapted to be slid outwardl into the air stream to form air brakes, r for sliding said air foils, supports for the rods,

spring pressed members frictionally holding said rods in retracted position against said supports, a lever, a cable carried by the lever connecting said spring pressed members together, and means on said lever for operatin said cable to release said spring pressed members.

18. In an airplane, flexible air foils carried by the wings and adapted to be slid outwardly into the air stream to form air brakes, cables connected to the free edges of the air foils and t0 the wing structure for curving the foils forwardly when thrust into the air stream, rock shafts carried by the wing having crank arms, rods connected to said crank arms and to air foils for sliding said air foils outwardly and inwardly when said rock shafts are'actuated,;and an operating lever connected to said rock shafts.

In testimony whereof I aflix my signature.

RICHARD MICEK. [L. 5.] 

